Gas turbine engine with inspection port and method for using the same

Abstract

A gas turbine engine is provided that includes a compressor section, a combustor section, a turbine section, and an inspection port. The turbine section includes a rotor stage and a stator vane stage. A core gas path extends through the compressor section, the combustor section, and the turbine section. The inspection port is disposed within the turbine section. The inspection port is configured to provide access through a portion of the core gas path that extends within the turbine section and to a component disposed radially inside of the portion of the core gas path that extends within the turbine section.

1 . A gas turbine engine, comprising: 
 a compressor section;   a combustor section;    a turbine section having a rotor stage and a stator vane stage;    a core gas path extending through the compressor section, the combustor section, and the turbine section; and   an inspection port disposed within the turbine section, wherein the inspection port is configured to provide access through a portion of the core gas path that extends within the turbine section and to a component disposed radially inside of the portion of the core gas path that extends within the turbine section.   
     
     
         2 . The gas turbine engine of  claim 1 , wherein the inspection port includes an outer inspection port engaged with an outer radial boundary structure of the core gas path that extends within the turbine section, and an inner inspection port engaged with an inner radial boundary structure of the core gas path that extends within the turbine section. 
     
     
         3 . The gas turbine engine of  claim 2 , wherein the outer inspection port includes an outer inspection port access passage and an outer inspection port plug, and the inner inspection port includes an inner inspection port access passage and an inner inspection port plug. 
     
     
         4 . The gas turbine engine of  claim 3 , wherein the outer radial boundary structure of the core gas path that extends within the turbine section includes an engine case. 
     
     
         5 . The gas turbine engine of  claim 4 , wherein the outer radial boundary structure of the core gas path core gas path that extends within the turbine section includes a stator vane outer platform. 
     
     
         6 . The gas turbine engine of  claim 3 , wherein the inner radial boundary structure of the core gas path that extends within the turbine section includes a stator vane inner platform. 
     
     
         7 . The gas turbine engine of  claim 3 , wherein the outer inspection port access passage and the inner inspection port access passage are aligned with one another.  
     
     
         8 . The gas turbine engine of  claim 2 , wherein the outer inspection port and the inner inspection port are disposed circumferentially between a pair of adjacent vanes of the stator vane stage.  
     
     
         9 . The gas turbine engine of  claim 1 , wherein at least a portion of the inspection port extends through a vane of a stator vane stage.  
     
     
         10 . The gas turbine engine of  claim 9 , wherein the at least said portion of the inspection port extending through the vane of the stator vane stage, or the vane, defines a passage configured to prevent transfer of gas between the passage and an interior region of the vane. 
     
     
         11 . A method of inspecting a component within a gas turbine engine, wherein the component comprises a solid metallic material, the method comprising: 
 extending a transducer through an inspection port that provides access through a core gas path of the gas turbine engine to a component disposed radially inside of the core gas path, wherein the transducer is configured to perform an inspection of a metallic component disposed radially inside of the core gas path;    providing a baseline inspection response signal that is produced by using the transducer to perform an initial inspection of the metallic component, the initial inspection including transmitting a first initial signal into the metallic component and sensing the metallic component for a second initial signal produced as a result of the first initial signal being transmitted into the metallic component, wherein the baseline inspection response signal is representative of the second initial signal and is unique to the metallic component;    using the transducer to inspect the metallic component, the inspection including transmitting a first signal into the metallic component and sensing the metallic component for a second signal produced as a result of the first signal being transmitted into the metallic component, and producing an inspection response signal representative of the second signal; and   evaluating the inspection response signal to determine the presence or absence of a defect in the metallic component using the baseline response signal.   
     
     
         12 . The method of  claim 11 , wherein the inspection port includes an outer inspection port engaged with an outer radial boundary structure of the core gas path, and an inner inspection port engaged with an inner radial boundary structure of the core gas path. 
     
     
         13 . The method of  claim 12 , wherein the outer inspection port includes an outer inspection port access passage and an outer inspection port plug, and the inner inspection port includes an inner inspection port access passage and an inner inspection port plug. 
     
     
         14 . The method of  claim 13 , wherein the outer radial boundary structure of the core gas path includes an outer casing and a stator vane outer platform. 
     
     
         15 . The method of  claim 13 , wherein the inner radial boundary structure of the core gas path includes a stator vane inner platform. 
     
     
         16 . The method of  claim 13 , wherein the outer inspection port access passage and the inner inspection port access passage are aligned with one another.  
     
     
         17 . The method of  claim 12 , wherein the outer inspection port and the inner inspection port are disposed circumferentially between a pair of adjacent vanes within a stator vane stage.  
     
     
         18 . The method of  claim 11 , wherein at least a portion of the inspection port extends through a vane of a stator vane stage.  
     
     
         19 . The method of  claim 18 , wherein the component is a disk of a rotor stage. 
     
     
         20 . A gas turbine engine, comprising: 
 a compressor section;   a combustor section;    a turbine section having a rotor stage and a stator vane stage;    a core gas path extending through the compressor section, the combustor section, and the turbine section; and   an inspection port disposed within the compressor section, wherein the inspection port is configured to provide access through a portion of the core gas path that extends within the compressor section and to a component disposed radially inside of the portion of the core gas path that extends within the compressor section.